NACELLE ASSEMBLY, GAS TURBINE ENGINE, AND METHOD OF INCREASING EFFECTIVE BOUNDARY LAYER THICKNESS OF INLET LIP SECTION OF NACELLE

摘要

PROBLEM TO BE SOLVED: To provide a fan nacelle assembly of a turbofan gas turbine engine, which is aerodynamically optimized for particular flight conditions. SOLUTION: The nacelle assembly 26 includes an inlet lip section 38 and a cowl section 50 downstream of the inlet lip section. The cowl section includes a flexible portion 52 which is selectively expanded or retracted adjacent the inlet lip section 38. The flexible portion 52 is located within an exterior wall 55 of the nacelle assembly 26. The flexible portion 52 transforms the cowl section 50 behind the inlet lip tip section 38 in response to a detected operability condition. A sensor 61 detects the operability condition and communicates with a controller 62 to adjust the flexible portion 52 of the cowl section 50 into a desired shape. The actual shape of the flexible portion 52 of the cowl section 50 will vary depending on specific design parameters including the operability conditions experienced by the aircraft. COPYRIGHT: (C)2009,JPO&INPIT